Aeroplane.



L, A. HAYOT.

AEROPLANE.

APPLIOATION FILED AUG. 31, 1909.

Patented Nov. 29, 1910.

2 SHEETS-SHEET 1.

WI TI ESSFJ LAILUlls-u 244. AERONAUTICS L. A. HAYOT.

AEROPLANE.

APPLICATION FILED AUG. 31, 1909.

976,876. Patented N0v.29, 1910.

2 SHEETS-SHEET 2.

HEHUNHU l Lil throne...

LOUIS ADOLPI-IE HAYOT, OF BEAUVAIS, FRANCE.

AEROPLANE.

erases.

To all whom it may concern:

Be it known that I, LOUIS ADOLPHE HAYoT, a citizen of the French Republic, residing at 16 Rue de Saint-Quentin, Beauvais, in the Department of Oise, France, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to aeroplanes and the present improvements have for their object to provide an aeroplane which shall be selfequilibrating and in which the supporting planes are constructed and arranged in such a manner that they will be capable of obeying readily the external forces and their own inertia. This result is obtained by a displacement of these planes in the direction of the length of the apparatus, whereby the planes are caused to move parallel to themselves so that their angle with the axis of the spindle-shaped hull of the aeroplane shall remain unaltered.

In the accompanying drawings :Figure 1 is a longitudinal elevation of the aeroplane, the spindle-shaped hull being shown in section for the sake of clearness. Fig. 2

is an end view of the aeroplane; Fig. 3 is a plan thereof; Figs. 4 and 5 show details. Fig. 6 is an enlarged detail view.

The improved aeroplane comprises, like the other known machines, a spindle-shaped hull a mounted on a carriage of a suitable type having steerable wheels.

The screw propeller, or screw propellers Z) which may be located in front as shown, are arranged so that the propelling force passes through the center of gravity of the body of the machine. This expression body of the machine as used in this specification is intended to include: the spindle-shaped hull, the carrying wheels, the screw propeller or screw propellers, the radiator, &c., in a word all those parts which are suspended from the planes.

The weight is distributed to suit the re quirements of the present improvements, and also so as to make the moment of inertia of the body of the machine as large as possible in relation to the transverse axis passing through its center of gravity at right angles to its plane of symmetry.

The parts such as the wheels, rudders, the radiator, &c., which are located outside the spindle-shaped hull, are also distributed in such a manner that the resultant of their resistance to forward motion will pass through Specification of Letters Patent.

Application filed August 31, 1909.

Patented Nov. 29, 1910. Serial No. 515,520.

the center of gravity of the body of the machine.

The supporting apparatus consists of groups of wings l, 2, 3 each group comprismg one or more wings, the wings of each group 1, 2, &c., being preferably located in such a manner that the wings of one group shall not be situated in the wake of those of the preceding group. The supporting surfaces also act as steadying devices and as devices for deadening oscillation. They are therefore grouped (preferably toward the ends of the body of the machine) in such a manner as to be located as far away as possible from the center of gravity and to have a more efiicient action.

Each group 1, 2, &c., comprises one or more superposed wings each wing forming a V or very open dihedral angle of small spread, and narrow in the direction of forward motion so as to reduce the displacements of the center of pressure.

Each wing is constituted by two longitudinals c, d as shown in the partial plan 8 (Fig. 4) arranged in the direction of the spread, and on which are fixed in the known manner incurved transverse ribs f according to the desired profile of the wing (Fig. 1).

The essential feature of the present invention is the connecting means between the planes and the body of the machine. The nature of this connecting means is such that the planes can obey readily the external forces and their own inertia by moving parallelly to themselves in the direction of the length of the apparatus, the angle made by the wings with the axis of the body of the machine consequently remaining unaltered. A connecting means of this kind may be constructed in many ways, preferably as follows :The wings are jointed at r1",ss, by means of their longitudinals 0 (Z to their supports constituted for instance by one or more groups of parallel rods m m n n. located in planes parallel to the plane of the longitudinal axis of the apparatus. The wings are further maintained equidistant and supported by shrouds f and 9 (Fig. 2).

The rods m n &c., with their shrouds are jointed to the spindle-shaped hull a by means of trunnions 7L h &o., onwhich they are capable of oscillating freely. These trunnions are arranged on the hull a at points such that the center of the parallel forces due to the reactions of the parallel rods m 17. acting thereon, shall coincide,

during normal flight at the ordinary speed, with the center of gravity of the body of the machine.

When the horizontal rudder is also a means of support, then the reaction exerted by the said rudder upon its axis parallel to the rods m 41. must be reckoned in the number of the parallel forces acting upon the body of the machine.

The trunnions are fixed on the hull in such a manner that they can be readily displaced for the purpose of centering the aeroplane, that is to say, for bringing the two centers in question into coincidence, and also for altering slightly according to circumstances the inclination of the wings on the body of the machine.

As shown in Fig. 6 the uprights o of the hull a, are provided with a plurality of holes m which allow the trunnions to be mounted at variable heights with respect to the uprights. By mounting the rods on different uprights the positions of the rods with respect to the length of the hull may be varied.

By construction the figure formed by two rods m m for example, the line joining their trunnions 71. 7L and the line r r oining the joints of any one of the wings on the rods is a parallelogram h --r r h (Fig. 1).

The result of this construction is that whether the planes are directed forward or to the rear, the angle of the wings with the axis of the body of the machine remains the same as indicated in the diagram (Fig. 5), where the inclination is assumed to be directed toward the rear, and the dash-dot lines represent the inclined planes; the angle has remained constant.

The group of wings 1, 2, 3, &c., are connected together and their displacements are maintained equal and simultaneous by means of longitudinal bars j parallel to the axis of the body of the machine and jointed to the forward rods m, m &c. of each group. The figure formed by a bar 7', the rods m m jointed together by the latter, and the line of the joints 7L2, 7L of these rods with the hull, is therefore also a jointed parallelogram.

The planes are supported in the position of rest by stops i on the frame or by any other means which will prevent them from folding back of themselves completely on to the hull.

The various arrangements hereinbefore described are designed to satisfy the theoretical conditions of equilibrium which characterize this type of aeroplane, and which should be approximated as closely as pos sible. These conditions are the following During normal flight at the ordinary speed, the center of the system of the parallel forces that act upon the trunnions (and also upon the axis of the horizontal rudder if the lat- 1. In an aeroplane, the combination with i the wings and the body of the machine, of means connecting the wings and the body of the machine, whereby each wing can move freely parallel to itself in the direction of the length of the apparatus to occupy any one of a plurality of positions in different planes parallel to the normal plane of the wings, as set forth.

2. In an aeroplane, the combination with the wings and the body of the machine of parallel vertically extending supports arranged in groups of two, in the direction of the length of the aeroplane, said supports being jointed to the body of the machine, and means jointing the wings to said sup ports whereby each wing can move freely, said parts being so positioned and arranged that the line joining the joints of each wing with the two supports forming a group, the two parallel supports forming said group, and the line joining the joints of said two parallel supports with the body of the machine forms a jointed parallelogram.

3. In an aeroplane, the combination with the bot y of the machine, of a series of groups of wings, rods supporting said wings, and bars jointed to the forward supporting rods of the wings and connecting two successive groups of wings, said bars being parallel to the axes of the corresponding joints, whereby a jointed bar, the rods and corresponding joints constitute a jointed parallelogram, for the purpose of insuring a simultaneous displacement of the whole of the planes of the aeroplane, as set forth.

1. In an aeroplane of the type specified, the combination with a spindle-shaped hull, of wings for supporting said hull, wing supports, joints connecting said wing supports to said hull, located at points such that the center of the system of parallel forces acting through said supports, shall coincide during normal flight at the ordinary speed, with the center of gravity of the body of the machine, as set forth.

5. In an aeroplane of the type specified, the combination with a spindle-shaped hull, of wings for supporting said hull, wing supports, a horizontal rudder acting as a means of support and joints connecting said wing supports to said hull, so located that the LF-h HEHUHHU l mu center of the system of parallel forces acting through said supports, shall coincide during normal flight at the ordinary speed with the center of gravity of the machine, the reaction acting upon the axis of said horizontal rudder parallelly to said Wing supports being comprised in the said system of parallel forces, as set forth.

In testimony whereof I have signed my name to this specification in the presence "of'io two subscribing Witnesses.

LOUIS ADOLPHE HAYOT.

Witnesses:

Louis FAUTRAT, H. G. Coxn. 

